GOE 769 AIRFOIL (goe769-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 769 AIRFOIL (goe769-il) Reynolds number: 50,000 Max Cl/Cd: 28.86 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe769-il-50000-n5.txt Download as CSV file: xf-goe769-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 769 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.1979 0.10421 0.09771 -0.0233 1.0000 0.1336
-8.000 -0.1940 0.10177 0.09539 -0.0234 1.0000 0.1348
-7.750 -0.1928 0.09954 0.09331 -0.0234 1.0000 0.1361
-7.500 -0.1958 0.09773 0.09167 -0.0230 1.0000 0.1380
-7.000 -0.2020 0.08644 0.08044 -0.0396 0.9460 0.0941
-6.750 -0.1698 0.08245 0.07640 -0.0428 0.9246 0.0919
-6.250 -0.1344 0.07122 0.06492 -0.0586 0.8785 0.0837
-6.000 -0.1157 0.06738 0.06097 -0.0622 0.8579 0.0827
-5.750 -0.1004 0.06345 0.05688 -0.0655 0.8386 0.0816
-5.500 -0.0878 0.05957 0.05282 -0.0682 0.8202 0.0810
-5.250 -0.0751 0.05588 0.04891 -0.0704 0.8028 0.0814
-5.000 -0.0613 0.05228 0.04503 -0.0721 0.7870 0.0821
-4.750 -0.0458 0.04871 0.04109 -0.0735 0.7728 0.0828
-4.500 -0.0290 0.04542 0.03740 -0.0742 0.7587 0.0833
-4.250 -0.0112 0.04246 0.03403 -0.0744 0.7443 0.0838
-4.000 0.0089 0.03951 0.03051 -0.0744 0.7319 0.0846
-3.750 0.0309 0.03830 0.02922 -0.0736 0.7179 0.0864
-3.500 0.0530 0.03699 0.02769 -0.0730 0.7039 0.0891
-3.250 0.0769 0.03516 0.02536 -0.0724 0.6924 0.0922
-3.000 0.1002 0.03356 0.02337 -0.0717 0.6788 0.0946
-2.750 0.1245 0.03265 0.02236 -0.0709 0.6663 0.0975
-2.500 0.1502 0.03159 0.02096 -0.0702 0.6542 0.1025
-2.250 0.1752 0.03075 0.01996 -0.0695 0.6412 0.1072
-2.000 0.2024 0.02996 0.01889 -0.0688 0.6307 0.1136
-1.750 0.2272 0.02935 0.01822 -0.0681 0.6170 0.1203
-1.500 0.2543 0.02875 0.01736 -0.0674 0.6059 0.1300
-1.250 0.2803 0.02827 0.01689 -0.0667 0.5938 0.1398
-1.000 0.3068 0.02783 0.01639 -0.0661 0.5817 0.1516
-0.750 0.3346 0.02738 0.01580 -0.0654 0.5708 0.1658
-0.500 0.3606 0.02711 0.01550 -0.0647 0.5580 0.1813
-0.250 0.3877 0.02674 0.01503 -0.0640 0.5477 0.1992
0.000 0.4127 0.02653 0.01486 -0.0632 0.5351 0.2191
0.250 0.4380 0.02626 0.01464 -0.0624 0.5241 0.2441
0.500 0.4632 0.02593 0.01440 -0.0615 0.5134 0.2800
0.750 0.4864 0.02553 0.01435 -0.0606 0.5026 0.3467
1.250 0.5606 0.02405 0.01413 -0.0624 0.4797 1.0000
1.500 0.5857 0.02430 0.01403 -0.0614 0.4710 1.0000
1.750 0.6085 0.02474 0.01429 -0.0604 0.4603 1.0000
2.000 0.6333 0.02503 0.01430 -0.0594 0.4517 1.0000
2.250 0.6558 0.02550 0.01463 -0.0584 0.4413 1.0000
2.500 0.6806 0.02583 0.01471 -0.0575 0.4333 1.0000
2.750 0.7024 0.02638 0.01518 -0.0565 0.4232 1.0000
3.000 0.7279 0.02668 0.01521 -0.0556 0.4156 1.0000
3.250 0.7484 0.02736 0.01587 -0.0545 0.4054 1.0000
3.500 0.7736 0.02769 0.01597 -0.0537 0.3982 1.0000
3.750 0.7936 0.02845 0.01673 -0.0526 0.3888 1.0000
4.000 0.8175 0.02889 0.01701 -0.0517 0.3813 1.0000
4.250 0.8384 0.02960 0.01766 -0.0507 0.3731 1.0000
4.500 0.8599 0.03025 0.01825 -0.0498 0.3653 1.0000
4.750 0.8850 0.03067 0.01847 -0.0490 0.3593 1.0000
5.000 0.9015 0.03172 0.01961 -0.0478 0.3508 1.0000
5.250 0.9245 0.03225 0.02002 -0.0469 0.3444 1.0000
5.500 0.9446 0.03307 0.02081 -0.0459 0.3380 1.0000
5.750 0.9616 0.03410 0.02188 -0.0447 0.3310 1.0000
6.000 0.9850 0.03463 0.02229 -0.0439 0.3256 1.0000
6.250 1.0019 0.03570 0.02339 -0.0428 0.3197 1.0000
6.500 1.0161 0.03691 0.02467 -0.0414 0.3133 1.0000
6.750 1.0382 0.03755 0.02523 -0.0406 0.3085 1.0000
7.000 1.0566 0.03852 0.02617 -0.0396 0.3038 1.0000
7.250 1.0620 0.04035 0.02818 -0.0378 0.2978 1.0000
7.500 1.0785 0.04136 0.02919 -0.0367 0.2931 1.0000
7.750 1.1047 0.04172 0.02941 -0.0361 0.2893 1.0000
8.000 1.0992 0.04429 0.03221 -0.0339 0.2842 1.0000
8.250 1.0959 0.04664 0.03471 -0.0318 0.2795 1.0000
8.500 1.1096 0.04777 0.03582 -0.0306 0.2756 1.0000
8.750 1.1412 0.04780 0.03572 -0.0303 0.2725 1.0000
9.000 1.0755 0.05451 0.04281 -0.0266 0.2676 1.0000
9.250 0.9895 0.06646 0.05509 -0.0288 0.2601 1.0000
9.500 1.0150 0.06638 0.05494 -0.0276 0.2578 1.0000
9.750 1.0596 0.06413 0.05258 -0.0256 0.2562 1.0000
10.250 0.8409 0.10496 0.09397 -0.0435 0.2327 1.0000
10.500 0.8436 0.10849 0.09752 -0.0443 0.2291 1.0000
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Polar data table (+)
Polar graphs
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